36624 Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 / Proposed Rules

on the States, on the relationship

between the national government and

the States, or on the distribution of

power and responsibilities among the

various levels of government. Therefore,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, will not have a significant

economic impact, positive or negative,

on a substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend part

39 of the Federal Aviation Regulations

(14 CFR part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Airbus Industrie: Docket 97–NM–307–AD.

Applicability: All Model A300, A310, and

A300–600 series airplanes; certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To detect and correct cracked or broken

door stop fittings of the forward passenger

doors, which could result in failure of the

door stop fittings, consequent reduced

structural integrity of the door support

structure, and sudden loss of cabin pressure

in the passenger compartment, accomplish

the following:

(a) Prior to the accumulation of the total

flight cycles specified in the ‘‘Threshold’’

column of paragraph 1.B.(5) of the Planning

Information of Airbus Service Bulletin A300–

53–0309 (for Model A300 series airplanes);

A310–53–2087 (for Model A310 series

airplanes); or A300–53–6060 (for Model

A300–600 series airplanes); all dated March

19, 1997; as applicable; or within 200 flight

cycles after the effective date of this AD,

whichever occurs later; accomplish

paragraphs (a)(1) and (a)(2) of this AD.

(1) Perform a visual inspection of the left

and right forward passenger door stop fittings

to detect cracked or broken door stop fittings,

in accordance with the applicable service

bulletin. And

(2) Thereafter, repeat the visual inspection

at the intervals specified in the ‘‘Intervals’’

column of paragraph 1.B.(5) of the Planning

Information of the applicable service

bulletin.

(b) If any cracked or broken door stop

fitting is detected during any inspection

required by paragraph (a)(1) or (a)(2) of this

AD, prior to further flight, replace the door

stop fitting with a new fitting in accordance

with Airbus Service Bulletin A300–53–0309

(for Model A300 series airplanes); A310–53–

2087 (for Model A310 series airplanes); or

A300–53–6060 (for Model A300–600 series

airplanes); all dated March 19, 1997; as

applicable. Thereafter, repeat the visual

inspections at the intervals specified in the

‘‘Intervals’’ column of paragraph 1.B.(5) of

the Planning Information of the applicable

service bulletin.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Note 3: The subject of this AD is addressed

in French airworthiness directive 97–124–

223(B), dated June 4, 1997.

Issued in Renton, Washington, on June 30,

1998.

Stewart R. Miller,

Acting Manager,

Transport Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–17958 Filed 7–6–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–96–AD]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Dornier Model 328–100 series

airplanes. This proposal would require

a one-time inspection of direct current

(DC) power unit 1VE to determine

whether electrical connections are

correctly installed and stud nuts are

correctly torqued, and corrective

actions, if necessary. For certain

airplanes, this proposal also would

require replacement of the existing DC

power unit 1VE with a modified DC

power unit. This proposal is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to prevent overheating of

electrical connections, which could

result in electrical arcing and

consequent fire.

DATES: Comments must be received by

August 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

96–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

FAIRCHILD DORNIER, DORNIER

Luftfahrt GmbH, P.O. Box 1103, D–

82230 Wessling, Germany. This

information may be examined at the
Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 / Proposed Rules 36625

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–M–96–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

98–NM–96–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Luftfahrt-Bundesamt (LBA),

which is the airworthiness authority for

Germany, notified the FAA that an

unsafe condition may exist on certain

Dornier Model 328–100 series airplanes.

The LBA advises that it has received

reports of overheating of the electrical

connection studs on direct current (DC)

power unit 1VE, which has been

attributed to incorrectly installed

terminals and spring washers, and

incorrect torquing of the stud nuts. The

LBA also has received reports of

overheating and burning of the

mounting plate of the bus bar of the

auxiliary power unit in the DC power

unit 1VE, which have been attributed to

an incorrectly torqued bus bar screw.

Such overheating of electrical

connections, if not corrected, could

result in electrical arcing and

consequent fire.

Explanation of Relevant Service

Information

The manufacturer has issued Dornier

Alert Service Bulletin ASB–328–24–

018, dated August 5, 1997. The alert

service bulletin describes procedures for

a one-time visual inspection of the

electrical connections of DC power unit

1VE to determine whether terminals and

spring washers are installed correctly,

and a one-time torque inspection of the

stud nuts to determine whether they are

torqued correctly. Figure 1 and Table 1

of this alert service bulletin specify

criteria for ensuring correct installation

of the terminals and spring washers and

correct torquing of the stud nuts.

The manufacturer also has issued

Dornier Alert Service Bulletin ASB–

328–24–021, dated November 25, 1997,

which describes procedures for

removing DC power unit 1VE and

installing a modified DC power unit.

Dornier Alert Service Bulletin ASB–

328–24–021 refers to l’Equipement et la

Construction Electrique (ECE) Alert

Service Bulletin ASB 230GC02Y–24–

001, dated November 24, 1997, as an

additional source of service information

for accomplishing the modification of

the DC power unit. That ECE alert

service bulletin describes procedures for

inspecting the glass mounting plate of

the auxiliary power unit (APU) bus bar

in the DC power unit 1VE for heat

damage, installing a shim, and

performing a one-time inspection of the

APU bus bar screw to ensure that it is

correctly torqued.

Accomplishment of the actions

specified in the Dornier alert service

bulletins is intended to adequately

address the identified unsafe condition.

The LBA classified these Dornier alert

service bulletins as mandatory and

issued German airworthiness directive

97–322, dated November 20, 1997, and

German airworthiness directive 97–354,

dated December 18, 1997, in order to

assure the continued airworthiness of

these airplanes in Germany.

FAA’s Conclusions

This airplane model is manufactured

in Germany and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the LBA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the LBA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the Dornier alert service bulletins

described previously.

Cost Impact

The FAA estimates that 50 airplanes

of U.S. registry would be affected by this

proposed AD.

It would take approximately 1 work

hour per airplane to accomplish the

proposed inspection, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of this

proposed inspection on U.S. operators is

estimated to be $3,000, or $60 per

airplane.

It would take approximately 4 work

hours per airplane to accomplish the

proposed replacement, at an average

labor rate of $60 per work hour.

Required parts would be provided by

the manufacturer at no cost to the

operators. Based on these figures, the

cost impact of this proposed

replacement on U.S. operators is

estimated to be $12,000, or $240 per

airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

Regulatory Impact

The regulations proposed herein

would not have substantial direct effects

on the States, on the relationship

between the national government and

the States, or on the distribution of

power and responsibilities among the

various levels of government. Therefore,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.
36626 Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 / Proposed Rules

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, will not have a significant

economic impact, positive or negative,

on a substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend part

39 of the Federal Aviation Regulations

(14 CFR part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Dornier Luftfahrt GmbH: Docket 98–NM–

96–AD.

Applicability: Model 328–100 series

airplanes, as listed in Dornier Alert Service

Bulletin ASB–328–24–021, dated November

25, 1997; or Dornier Alert Service Bulletin

ASB–328–24–018, dated August 5, 1997;

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent overheating of electrical

connections, which could result in electrical

arcing and consequent fire, accomplish the

following:

(a) For airplanes listed in Dornier Alert

Service Bulletin ASB–328–24–018, dated

August 5, 1997: Within 10 days after the

effective date of this AD, perform the actions

required by paragraphs (a)(1) and (a)(2) of

this AD, in accordance with Dornier Alert

Service Bulletin ASB–328–24–018, dated

August 5, 1997.

(1) Perform a one-time visual inspection of

direct current (DC) power unit 1VE to

determine whether electrical connections are

installed correctly, in accordance with the

Accomplishment Instructions of the alert

service bulletin. If any discrepancy is

detected, prior to further flight, install the

connections in accordance with Figure 1 of

the alert service bulletin.

(2) Perform a one-time torque inspection of

the stud nuts of DC power unit 1VE to

determine whether they are torqued

correctly, in accordance with the

Accomplishment Instructions of the alert

service bulletin. If any discrepancy is found,

prior to further flight, torque in accordance

with Table 1 of the alert service bulletin.

(b) For airplanes listed in Dornier Alert

Service Bulletin ASB–328–24–021, dated

November 25, 1997: Within 10 days after the

effective date of this AD, replace the existing

DC power unit 1VE with a modified DC

power unit, in accordance with Dornier Alert

Service Bulletin ASB–328–24–021, dated

November 25, 1997.

Note 2: Dornier Alert Service Bulletin 328–

24–021, dated November 25, 1997, refers to

l’Equipement et la Construction Electrique

Alert Service Bulletin ASB 230GC02Y–24–

001, dated November 24, 1997, as an

additional source of service information for

accomplishing the modification of the DC

power unit.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Note 4: The subject of this AD is addressed

in German airworthiness directive 97–322,

dated November 20, 1997; and German

airworthiness directive 97–354, dated

December 18, 1997.

Issued in Renton, Washington, on June 30,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17957 Filed 7–6–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–158–AD]

RIN 2120–AA64

Airworthiness Directives; Aerospatiale

Model SN–601 (Corvette) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to all

Aerospatiale Model SN–601 (Corvette)

series airplanes. This proposal would

require repetitive inspections to detect

corrosion, cracking, or rupture of the

support arms of the aileron balance

weights; and repair, if necessary.

Accomplishment of the repair would

terminate the repetitive inspection

requirement of this AD. This proposal is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by the proposed

AD are intended to prevent corrosion,

cracking, or rupture of the support arms

of the aileron balance weights, which

may cause reduced flutter damping or

jamming of the aileron, and consequent

reduced controllability of the airplane.

DATES: Comments must be received by

August 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

158–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Aerospatiale, 316 Route de Bayonne,

31060 Toulouse, Cedex 03, France. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.